• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a feed arm (112) for a multi-circuit fuel injector (110) of a gas turbine. The arm includes an elongate tubular sleeve (124) having a central bore with an inner wall defining an inner diameter, and an elongated fuel tube (122) positioned in the bore of the tubular sleeve. A main fuel flow passage (130) is formed in the tubular wall of the fuel tube and delimited by the inner wall of the tubular sleeve. The main fuel flow passage (130) includes a plurality of circumferentially spaced axial channels (132) extending a predetermined distance along the axial length of the fuel tube (122). A secondary fuel flow passage (134) extends through a central portion of the fuel tube. The fuel tube is configured to facilitate heat transfer by conduction and / or convection. Figure for the abstract: Fig 2
    公开号:FR3078550A1
    申请号:FR1902238
    申请日:2019-03-05
    公开日:2019-09-06
    发明作者:Brandon Philip Williams
    申请人:Delavan Inc；
    IPC主号:
    专利说明:

    Title of the invention: SUPPLY ARM FOR FUEL INJECTOR WITH MULTIPLE CIRCUITS Technical field of the invention The present invention relates to fuel injectors and, more particularly, a supply arm for a fuel injector to multiple circuits of a gas turbine.
    STATE OF THE ART [0002] In gas turbines, the fuel injectors convey fuel under pressure from a fuel distribution manifold to one or more combustion chambers. The fuel injectors also operate to prepare the fuel for mixing with the air before combustion. Each injector typically includes an inlet port located near the fuel delivery manifold, one or more tubular fuel passages, and an outlet port connected to a spray nozzle for introducing atomized fuel into a combustion chamber. The atomized fuel is then typically mixed with air and ignited, and the resulting expanded gas causes a plurality of turbine blades to rotate, thereby providing the energy necessary to propel an aircraft, or others. applications.
    A large number of fuel injectors include multiple fuel flow passages to more easily regulate the output power of the gas turbine. For example, a fuel injector may have a main fuel flow passage and a secondary fuel flow passage, both passages being used during high power operation and only the main flow passage of fuel being used during operation at a lower power level.
    Fuel injectors also typically include thermal jackets surrounding the tubular fuel passages to protect the fuel flowing through the passages from the extreme heat generated in the combustion chamber. These thermal shirts are necessary to prevent coking, which is the breakdown of liquid fuel into solid deposits. Coking is likely to take place when the temperature of the walls wet in a fuel passage exceeds a maximum value. When coking takes place, solid deposits can also form inside the fuel flow passage, which restricts the flow of fuel through the passage and can render the fuel injector ineffective or unusable.
    Conventional multi-circuit fuel injectors include a tubular member with primary and secondary fuel flow passages. The main fuel flow passage is formed through a central portion of the tubular member and the secondary fuel flow passage is formed to surround the main fuel flow passage. Fuel flows continuously through the main fuel flow passage, however fuel may only flow intermittently through the secondary fuel flow passage. Depending on the operational requirements of the engine, the speed of fuel flow through the secondary passage may be reduced, or the flow may be completely stopped. As a result, stagnant fuel may be present in the secondary fuel flow passage. Since the flow velocity through the secondary passage is reduced, and since the secondary fuel flow passage is located very close to the extreme heat generated by the combustion chamber, coking of the fuel in the secondary passage Fuel flow is an ordinary problem.
    There is therefore a need for improved methods and systems for preventing coking in the two fuel flow passages, main and secondary, of fuel injectors for gas turbines.
    SUMMARY OF THE INVENTION Certain advantages of the present invention will emerge more clearly on reading the description below. Additional advantages of the invention will be implemented and achieved by the devices and methods presented in the written description and the claims, as well as in the accompanying drawings.
    To achieve these and other advantages, and in accordance with the object of the invention as it is carried out, a supply arm for a multi-circuit fuel injector of a gas turbine is proposed. The feed arm includes an elongated tubular sleeve having a central bore with an interior wall defining an internal diameter, and an elongated fuel tube positioned within the bore of the tubular sleeve. The fuel tube includes a tubular wall defining an outer diameter which is substantially equal to the inner diameter of the central bore. A main fuel flow passage is formed inside the tubular wall of the fuel tube and is bounded by the inner wall of the tubular sleeve, and the main fuel flow passage extends in the direction of the circumference around the fuel tube at least once along the axial length of the fuel tube. A secondary fuel flow passage extends through a central portion of the fuel tube, and the fuel tube is configured to facilitate heat transfer between the main fuel flow passage and the secondary flow passage fuel by conduction and / or convection.
    A method of forming a supply arm for a multi-circuit fuel injector of a gas turbine is also proposed. The method of forming a feed arm for a multi-circuit fuel injector of a gas turbine includes the steps of: providing a fuel tube having a tubular wall, a central passage and an outer diameter, forming a fuel flow passage in the tubular wall of the fuel tube such that the fuel flow passage winds in a circumferential direction around the tube at least once along the axial length of the tube fuel, providing an elongated tubular sleeve having a central bore defining an internal diameter, the internal diameter being substantially equal to the external diameter of the fuel tube; and positioning the fuel tube inside the central bore of the tubular sleeve.
    Those skilled in the art will better understand these characteristics and advantages, as well as others, of the multi-circuit fuel injector according to the present invention, as well as the manner in which the invention is assembled and used, at the Reading of the description below of the preferred embodiments made with reference to the drawings described below.
    Figures To make it easier for those skilled in the art concerned with the present invention, without resorting to superfluous experiments, how to manufacture and use the multi-circuit fuel injector of the present invention, preferred embodiments of the latter will be described below in detail, with reference to certain figures, in which:
    [Fig.l] Figure 1 is a side elevational view in partial cross section of a fuel injector constructed according to an exemplary embodiment of the present invention, showing an external helical fuel passage surrounding an internal passage fuel ;
    [Fig.2] Figure 2 is a side elevational view in partial cross section of a fuel injector constructed according to another exemplary embodiment of the present invention, showing a plurality of external axial fuel passages connected by a central annular passage;
    [Fig.3] Figure 3 is a cross-sectional view taken along line 3-3 of Figure 1, showing the internal fuel passage and part of the external helical fuel passage;
    [Fig.4] Figure 4 is a cross-sectional view taken along line 4-4 of Figure 2, showing the internal fuel passage and the external axial fuel passages;
    [Fig.5] Figure 5 is a perspective view of a fuel tube in which the external and internal fuel flow passages are formed according to the exemplary embodiment illustrated in Figure 1; and [FIG. 6] FIG. 6 is a perspective view of a fuel tube in which the external and internal fuel flow passages are formed according to the exemplary embodiment illustrated in FIG. 2.
    Detailed description With reference to the drawings, in which the identical reference numbers identify or represent similar features or structural elements of the various embodiments of the invention, FIGS. 1, 3 and 5 illustrate an exemplary embodiment of a multi-circuit fuel injector generally represented by the reference number 10. Other embodiments of the fuel injector are presented in FIGS. 2, 4 and 6, as will be described below. The now preferred embodiments of the invention, examples of which are illustrated in the accompanying drawings, will now be described in detail.
    The present invention relates to an innovative and useful method of forming multiple fuel flow passages in a fuel injector mainly designed for use in a gas turbine. A main fuel passage of the present invention is formed in the outer part of a tubular structure and has a reduced cross-sectional area compared to conventional fuel passages. This reduced cross-sectional area increases the speed of the fuel flow and hence the heat transfer coefficient (HTC) by convection. This increase in HTC reduces the local temperature of the wet walls for the passage of fuel, which helps prevent coking of the fuel in the fuel injector.
    As illustrated in Figure 1, the fuel injector 10 comprises a rod or elongated supply arm 12 (e). A mounting flange (not shown) can be provided at the upstream end portion 14 of the supply arm 12 to allow the fuel injector 10 to be attached to a wall of the combustion chamber. a gas turbine, in a conventional manner. An equipped nozzle 16 is positioned at a downstream end portion 18 of the supply arm 12. The equipped nozzle 16 supplies atomized fuel to the combustion chamber.
    A fuel intake port 20 is formed near the upstream end portion 14 of the fuel injector 10. The fuel intake port 20 receives fuel from a fuel pump ( not shown) associated with the engine at a given flow rate and temperature. The fuel intake port communicates with an elongated fuel tube 22, which is surrounded by an outer tubular sleeve 24. The outer tubular sleeve 24 includes an outer wall 26 and a bore which extends through a central portion of the tubular sleeve to form an inner wall 28. The external diameter of the tubular sleeve 24 is chosen so that it is only slightly greater than the external diameter of the elongated fuel tube 22, so that the fuel tube 22 s fits inside the bore of the tubular sleeve 24. In an exemplary embodiment, the fuel tube 22 is pressed into the bore of the tubular sleeve 24.
    A main fuel flow passage 30 is formed inside the elongated fuel tube 22. In a first exemplary embodiment, the main fuel flow passage 30 extends around the fuel tube 22 in the direction of the circumference, at least once along the axial length of the fuel tube 22. The inner wall 28 of the tubular sleeve 24 delimits the main fuel flow passage 30 and forms part of the wall of the main fuel flow passage 30.
    The main fuel flow passage 30 may include one or more helical channels formed inside the fuel tube 22 and winding one or more times around the fuel tube 22. An exemplary embodiment of a fuel injector comprising a helical fuel flow channel 32 is illustrated in FIGS. 1 and 3. The pitch of the helical channel 32 can be chosen so as to regulate the speed of flow through the channel. The pitch of the helical channel 32 is the distance covered by the channel along the longitudinal axis of the supply arm 12 for a complete revolution of the helical channel. Those skilled in the art will readily understand that when the other parameters are held constant, increasing the pitch of the helical channel results in reduced fuel flow rates in the main fuel flow passage, while increasing the pitch of the helical channel causes increased fuel flow velocities in the main fuel flow passage.
    The width of the helical channel 32 can be chosen or otherwise designed to obtain a desired speed of fuel flow for the fuel injector of the present invention. This flexibility gives the nozzle designer more control over the pressure drop across the injector without having to sacrifice the flow velocity gains and heat transfer coefficients achieved by reducing the available flow area fuel in the main passage according to the methodology of the present invention.
    As illustrated in Figure 3, a secondary fuel flow passage 34 is formed in a central part of the fuel tube 22 and it extends over the axial length of the fuel injector 10. In one mode As an exemplary embodiment, the secondary fuel flow passage 34 is a hollow cylindrical passage or bore extending through a central interior portion of the fuel tube 22. The fuel tube 22 is configured to facilitate heat transfer between the main fuel flow passage 30 and secondary fuel flow passage 34 both by conduction and by convection. In an exemplary embodiment, the fuel tube 22 is made of a material which has a high thermal conductivity to facilitate heat transfer between the main fuel flow passage 30 and the secondary fuel flow passage 34 For example, the fuel tube 22 can be made of any number of metal alloys known in the art for their high thermal conductivity. However, those skilled in the art will understand that a wide variety of materials of suitable thermal conductivity can be used to construct the fuel tube 22. In conventional designs of multi-circuit fuel injectors, the primary and secondary passages of Fuel flows are often formed using concentric tubes. Advantageously, the formation of the main fuel flow passage 30 and the secondary fuel flow passage 34 from a single fuel tube 22 eliminates the need to compensate for the difference in thermal expansion rates between the two concentric tubes , as is required in conventional multi-circuit fuel injectors.
    Referring to Figure 5, the fuel tube 22 is shown without the outer tubular sleeve 24 which surrounds it and the associated fuel injector structure. The fuel tube 22 includes an upper end 36 and a lower end 38 having a reduced circumference and forming an upper chamber 40 and a lower chamber 42 which form part of the main fuel flow passage 30. The outer walls of the chamber upper 40 and lower chamber 42 are formed by the outer tubular sleeve 24. During the operation of the fuel injector 10, the fuel flows from the fuel intake orifice 20 into the upper chamber 40 and at inside the helical channel 32 through a channel inlet 44. The fuel flows continuously through the helical channel 32, while it flows intermittently through the secondary fuel passage 34 formed in the fuel tube bore 22. As fuel flows through the helical channel 32, heat is transferred between the helical channel 32 and the secondary fuel flow passage 34 both by conduction and by convection. At the lower end 38 of the fuel tube 22, the fuel flowing in the main fuel flow passage 30 leaves the helical channel 32 and passes through the lower chamber 42 before entering the equipped nozzle 16. The fuel flowing in the secondary fuel flow passage 34 also flows in the equipped nozzle 16. The equipped nozzle 16 then atomizes the fuel and introduces it into the combustion chamber of the gas turbine.
    In an exemplary embodiment, the main fuel flow passage 30 ensures a continuous flow of fuel during the operation of the gas turbine engine. The fuel flow speed can be changed according to the power requirements during each engine operating phase. On the contrary, the flow of fuel through the secondary fuel flow passage 34 is non-continuous, i.e. the fuel flows through the secondary fuel flow passage 14 only during certain operations requiring an increase in the engine power. Therefore, the fuel in the secondary fuel flow passage may move very slowly or not at all.
    In conventional multi-circuit fuel injectors the low speed of fuel flow through the secondary fuel flow passage is often insufficient to correctly transfer the heat so as to move it away from the secondary flow passage prevent fuel from coking inside the fuel passage. The concentric tubes of conventional multi-circuit fuel injectors typically used an internal tube passage to form the main fuel passage and an annular external passage formed by the internal diameter of the external tube and the external diameter of the internal tube. This conventional design may be inadequate since the wall temperature of the fuel in the secondary passage may exceed the limits of the fuel, which may result in coking.
    The fuel injector 10 fades the disadvantages of these conventional designs in two ways. First, the secondary fuel flow passage 34 is formed in the central bore of the fuel tube 22 and is thus isolated from the high temperatures present in the combustion chamber and in the ambient air. In addition, the main fuel flow passage 30 surrounds the secondary fuel flow passage 34. The constant flow of fuel in the main fuel flow passage 30 is sufficient to prevent coking in the main fuel passage. fuel flow and at the same time allows heat transfer from the secondary fuel flow passage 34 to the main fuel flow passage 30 by convection. In an exemplary embodiment, the main fuel flow passage 30 and the secondary fuel flow passage 34 are further protected from the heat of the combustion chamber by the outer tubular sleeve 24 which comprises a material of thermal insulation.
    Another exemplary embodiment of a fuel injector according to the present invention is illustrated in FIGS. 2, 4, and 6, and it is generally represented by the reference number 110. As illustrated in FIG. 2, the fuel injector 110 comprises an elongated rod or supply arm 112, an upstream end portion 114 and an equipped nozzle 116 positioned on a downstream end portion 118 of the supply arm 112. These elements of the fuel injector 110 are similar to the elements described above with regard to the exemplary embodiment illustrated in FIG. 1.
    A fuel inlet 120 is formed near the upstream end portion 114 of the fuel injector 110. The fuel inlet 120 receives fuel from a fuel pump ( not shown) associated with the motor, at a given flow rate and at a given temperature. The fuel intake port 120 communicates with an elongated fuel tube 122 which is surrounded by an outer tubular sleeve 124. The outer tubular sleeve 124 includes an outer wall 126 and a bore which extends through a central portion of the tubular sleeve forming an interior wall 128. The external diameter of the tubular sleeve 124 is chosen so that it is only slightly greater than the external diameter of the elongated fuel tube 122, so that the fuel tube 122 s' fits inside the bore of the tubular sleeve 124. In an exemplary embodiment, the fuel tube 122 is stamped in the bore of the tubular sleeve 124.
    A main fuel flow passage 130 is formed in the elongated fuel tube 22. In an exemplary embodiment, the main fuel flow passage 130 extends in the direction of the circumference around the tube fuel 122 at least once along the axial length of the fuel tube 122. The inner wall 128 of the tubular sleeve 124 defines the main fuel flow passage 130 and forms part of the wall of the main flow passage fuel 130.
    The main fuel flow passage 130 comprises a plurality of axial channels 132 spaced apart in the direction of the circumference, which extend over the axial length of the fuel tube. The plurality of axial channels can be divided into an upper part 148 and a lower part 150. The upper part 148 and the lower part 150 may each comprise a plurality of axial channels 132 connected by a central annular channel 152. The central annular channel 152 may have a width (as measured along the axial length of the supply arm 112) which is greater than the width (as measured in a direction perpendicular to the axial length of the supply arm supply 112) of the axial channels 132 individual. In an exemplary embodiment, the width of the central annular channel 152 is greater than or equal to twice the width of the individual axial channels 132.
    As illustrated in Figure 4, a secondary fuel flow passage 134 is formed in a central part of the fuel tube 122 and it extends over the axial length of the fuel injector 110. In one mode As an exemplary embodiment, the secondary fuel flow passage 134 is a hollow cylindrical passage or bore extending through a central interior portion of the fuel tube 122. The fuel tube 122 is configured to facilitate heat transfer between the main fuel flow passage 130 and the secondary fuel flow passage 134 both by conduction and by convection.
    The axial channels 132 can be spaced equidistantly around the hollow cylindrical part forming the secondary fuel flow passage 134, as illustrated in FIG. 4. Other arrangements of the axial channels are also envisaged by this description. In an exemplary embodiment, the axial channels 132 of the upper part 148 can be aligned with the axial channels 132 of the lower part 150. In another exemplary embodiment, the axial channels can be offset. The axial channels 132 may also be arranged asymmetrically around the central portion of the fuel tube 122, and they may be unevenly spaced around the secondary fuel flow passage 134. The fuel tube 122 may include a plurality of annular channels similar to the central annular channel 152.
    Referring to Figure 6, the fuel tube 122 is illustrated as used in the exemplary embodiment of the fuel injector 110. In this view, the fuel tube 122 is illustrated without the outer tubular sleeve 124 and the surrounding structure of the fuel injector 110. The fuel tube 122 includes an upper end 136 and a lower end 138 having a reduced circumference and forming an upper chamber 140 and a lower chamber 142 which are part of the main fuel flow passage 130. The outer walls of the upper chamber 140 and the lower chamber 142 are formed by the outer tubular sleeve 124. During the operation of the fuel injector 110, the fuel flows from the fuel inlet port 120 through the upper chamber 140 and into the plurality of axial channels 132 of the upper part 148 of the fuel tube 122. The fuel then flows from the axial channels 146 of the upper part 148 inside the central annular channel 152. From the central annular channel 152, the fuel flows into the axial channels 132 of the lower part 150 from the fuel tube 122, through the lower chamber 142 and inside the equipped nozzle 116 where it is atomized and introduced into the combustion chamber of the gas turbine engine. As the fuel flows through the axial channels 132 and the other parts of the main fuel flow passage 130, heat is transferred between the main fuel flow passage 130 and the secondary flow passage of fuel 134, both by conduction and by convection.
    A method of forming a supply arm for a multi-circuit fuel injector of a gas turbine is also described here. This method includes the step of providing the elongated outer tubular sleeve 24 having a central bore defining an inner diameter formed by the inner wall 28 of the tubular sleeve
    24. A fuel tube 22 is also provided and it includes one or more fuel flow passages, such as the helical fuel flow passages 32 shown in Figure 1 and the hollow cylindrical passage shown in Figure 3. The fuel tube 22 is then positioned inside the central bore of the outer tubular sleeve 24. To produce the helical channel 32 forming the main fuel flow passage 30, the outer diameter of the fuel tube 22 is machined so as to create the helical path around the circumference of the external fuel tube. In an exemplary embodiment, the helical channel 32 is formed by a machining process, such as turning the fuel tube 22 on a lathe or a lathe. In another exemplary embodiment, the helical channel is formed by machining by electro-erosion (EDM, "Electronic Discharge Machining" in English). In yet another embodiment, the fuel flow passages in the fuel tube 22 are formed by a molding process. Similarly, the axial fuel channels 132 and the central annular channel 152 as described above, can be formed by machining, molding, or by other methods known in the art.
    The devices and methods of the present invention as described herein and illustrated in the drawings, provide a multi-circuit fuel injector for a gas turbine engine, preventing coking and allowing increased control fuel flow. Of course, the invention is not limited to the embodiments described above and shown, from which we can provide other modes and other embodiments, without departing from the scope of the invention .
    权利要求:
    Claims (1)
    [1" id="c-fr-0001]
    Supply arm (112) for a multi-circuit fuel injector (110) of a gas turbine, the supply arm comprising:
    at. an elongated tubular sleeve (124), having a central bore with an interior wall (128) defining an internal diameter;
    b. an elongated fuel tube (122) positioned within the bore of the tubular sleeve (124), the fuel tube having a tubular wall defining an outer diameter, wherein the outer diameter of the fuel tube is substantially equal to internal diameter of the central bore;
    vs. a main fuel flow passage (130) formed inside the tubular wall of the fuel tube (122) and delimited by the inner wall of the tubular sleeve (124), the main fuel flow passage (130 ) comprising a plurality of axial channels (132) spaced in the direction of the circumference extending a predetermined distance along the axial length of the fuel tube (122), and
    d. a secondary fuel flow passage (134) extending through a central portion of the fuel tube (122).
    The feed arm (112) of claim 1, wherein the fuel tube (122) is configured to facilitate heat transfer by conduction between the main fuel flow passage (130) and the secondary flow passage fuel (134).
    The supply arm (112) of claim 1, wherein the fuel tube (122) is configured to facilitate heat transfer between the main fuel flow passage (130) and the secondary fuel flow passage (134) by convection, as fuel flows through the main fuel flow passage.
    A feed arm (112) according to claim 1, wherein the sleeve (124) is a thermal insulation sleeve.
    A feed arm (112) according to claim 1, wherein the plurality of axial channels (132) comprises a plurality of channels [Claim 6] [Claim 7] [Claim 8] [Claim 9] [Claim 10] formed axial top in an upper part (148) of the supply arm, and a plurality of lower axial channels formed in a lower part (150) of the supply arm, the upper and lower axial channels being connected by a central annular channel (152) . The feed arm (112) of claim 5, wherein a width of the central annular channel (152) is greater than a width of each of the plurality of axial channels (132).
    The feed arm (112) of claim 1, wherein the plurality of axial channels (132) are spaced equidistant around the central portion of the fuel tube (122).
    Method of forming a supply arm (112) for a multi-circuit fuel injector (10) of a gas turbine engine, the method comprising the steps of:
    at. providing a fuel tube (122) having a tubular wall, a central passage and an outer diameter;
    b. forming a fuel flow passage (130) in the tubular wall of the fuel tube (122) comprising machining a plurality of axial passages extending a predetermined distance along an axial length of the fuel tube fuel (122);
    vs. providing an elongated tubular sleeve (124) having a central bore defining an internal diameter, the internal diameter being substantially equal to the external diameter of the fuel tube (122); and
    d. position the fuel tube (122) inside the central bore of the tubular sleeve.
    The method of claim 8, wherein the plurality of axial passages are spaced equidistant in the direction of the circumference around the central passage of the fuel tube.
    The method of claim 8, wherein the step of machining the fuel flow passage further comprises machining a central annular channel (152) connecting a plurality of upper axial passages to a plurality of lower axial passages .
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    同族专利:
    公开号 | 公开日
    GB2488694A|2012-09-05|
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    FR2927984A1|2009-08-28|
    US8443608B2|2013-05-21|
    GB2457807A|2009-09-02|
    GB2457807B|2012-10-31|
    DE102009010604B4|2020-07-16|
    JP5143048B2|2013-02-13|
    JP2009204301A|2009-09-10|
    GB0903079D0|2009-04-08|
    GB2488694B|2012-12-26|
    DE102009010604A1|2009-08-27|
    GB201208944D0|2012-07-04|
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    法律状态:
    2019-04-19| PLFP| Fee payment|Year of fee payment: 11 |
    2020-08-31| PLFP| Fee payment|Year of fee payment: 13 |
    2021-10-15| PLSC| Publication of the preliminary search report|Effective date: 20211015 |
    2022-01-20| PLFP| Fee payment|Year of fee payment: 14 |
    优先权:
    申请号 | 申请日 | 专利标题
    US12/072,356|US8443608B2|2008-02-26|2008-02-26|Feed arm for a multiple circuit fuel injector|
    US12/072356|2008-02-26|
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